Integration assessment of conceptual design and intake aerodynamics of a non-conventional air-to-ground fighter aircraft

Bravo-Mosquera, Pedro David; Abdalla, Alvaro Martins; Cerón-Muñoz, Hernán Darío; Catalano, Fernando Martini

doi:10.1016/j.ast.2019.01.059

Cited by 20 publications

(10 citation statements)

References 30 publications

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“… Alegoz and Yapicioglu (2019) proposed a MCDM method with IT2FAHP, using TOPSIS and goal programming for supplier selection. In addition to these articles, studies on unmanned aerial vehicles (UAV) have also been conducted ( Bravo-Mosquera et al, 2019 ; Bravo-Mosquera et al, 2017 ). Schwening and Abdalla (2014) proposed selection of agricultural aircraft based on Fuzzy AHP and Fuzzy TOPSIS.…”

Section: Literature Reviewmentioning

confidence: 99%

Aircraft selection by applying AHP and TOPSIS in interval type-2 fuzzy sets

Kiracı

Akan

2020

Journal of Air Transport Management

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The selection of the appropriate aircraft can bring competitive advantages to airlines, however, there are a number of factors which introduce a degree of uncertainty to the selection process. By removing this uncertainty, airlines can increase their chances of achieving their long-term goals. New Multi-Criteria Decision Making (MCDM) methods provide decision-makers with a satisfactory solution for choosing suitable aircraft. Therefore, we focused on the multi-dimensional evaluation and selection of the most suitable commercial aircraft alternatives by using new MCDM method. This article provides decision support to airline planners on the selection of commercial aircraft under uncertainty. In the study, unlike other studies in the literature on aircraft selection, the model presented here uses an Interval Type-2 Fuzzy Analytical Hierarch Process (IT2FAHP) and Interval Type-2 Fuzzy Technique for Order Preference by Similarity to an Ideal Solution (IT2FTOPSIS) hybrid methods. The proposed model for aircraft selection allows commercial airlines to evaluate the aircraft in terms of specific criteria: economic performance, technical performance, and environmental impact, and, as a result, it helps decision makers select appropriate aircraft in an uncertain environment. In addition to use by commercial airlines, the methods in the study can also be applied to the selection of training aircraft, cargo aircraft and military aircraft. Our findings show that the Airbus A321neo is the most suitable commercial aircraft in terms of technical aspects, economic aspects and environmental aspects for airlines.

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Section: Literature Reviewmentioning

confidence: 99%

Aircraft selection by applying AHP and TOPSIS in interval type-2 fuzzy sets

Kiracı

Akan

2020

Journal of Air Transport Management

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“…Although several boundary layer ingestion (BLI) configurations with flush mounted intakes with minimum or no offset have been proposed in the literature, some new civil and non-civil aircraft configurations are expected to employ more aggressive offset intakes. These include BLI configurations with relatively high S-duct offsets [26], aircrafts with dorsal mounted intakes [30] and embedded gas turbine intakes for the core engine in propulsive fuselage configurations. The S-duct configuration used in this study was previously investigated by Zachos et al [18].…”

Section: A Experimental Facility and S-duct Configurationmentioning

confidence: 99%

Novel Method for Evaluating Intake Unsteady Flow Distortion

Migliorini

Zachos

MacManus

2022

Journal of Propulsion and Power

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Closer integration between the airframe and the propulsion system is expected for future aircraft to reduce fuel consumption, emissions, weight and drag. The use of embedded or partially embedded propulsion systems will require the use of complex intakes. However, this can result in unsteady flow distortion which can adversely affect the propulsion system efficiency and stability. Relative to conventional measurement systems, time-resolved Particle Image Velocimetry provides sufficient spatial and temporal resolution to enable the development of new methods to assess unsteady flow distortion. This work proposes a novel analysis approach to assess the unsteady flow distortion. For an S-duct configuration, the method was successfully used to evaluate the unsteady flow distortion in terms of idealized incidence angle perturbations. This example showed peaks up to ± 30° incidence and a duration equivalent to the passing time of 3 blades. The introduction of a non-uniform total pressure profile at the S-duct inlet increased the probability of peak distortion events with higher magnitude. The method provides an estimate of the likelihood, magnitude and duration of distortion events and is a new way to evaluate flow distortion that could induce instabilities for the propulsion system.

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“…40, the magnitude of DC 60 for a generic S-duct depends on the Mach number at the entrance (after normal shock in our case), duct curvature, and its overall length. To compare the variation of distortion index, a recent one-engine close-air support airplane concept with an S-duct diffuser 43 is considered for study. Figure 18 shows the result.…”

Section: Grid Convergence Studymentioning

confidence: 99%

The inlet flow structure of a conceptual open-nose supersonic drone

Saheby

Shen

Hays

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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This study describes the aerodynamic efficiency of a forebody–inlet configuration and computational investigation of a drone system, capable of sustainable supersonic cruising at Mach 1.60. Because the whole drone configuration is formed around the induction system and the design is highly interrelated to the flow structure of forebody and inlet efficiency, analysis of this section and understanding its flow pattern is necessary before any progress in design phases. The compression surface is designed analytically using oblique shock patterns, which results in a low drag forebody. To study the concept, two inlet–forebody geometries are considered for Computational Fluid Dynamic simulation using ANSYS Fluent code. The supersonic and subsonic performance, effects of angle of attack, sideslip, and duct geometries on the propulsive efficiency of the concept are studied by solving the three-dimensional Navier–Stokes equations in structured cell domains. Comparing the results with the available data from other sources indicates that the aerodynamic efficiency of the concept is acceptable at supersonic and transonic regimes.

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Integration assessment of conceptual design and intake aerodynamics of a non-conventional air-to-ground fighter aircraft

Cited by 20 publications

References 30 publications

Aircraft selection by applying AHP and TOPSIS in interval type-2 fuzzy sets

Aircraft selection by applying AHP and TOPSIS in interval type-2 fuzzy sets

Novel Method for Evaluating Intake Unsteady Flow Distortion

The inlet flow structure of a conceptual open-nose supersonic drone

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